US10550723B2 - Axially-partitioned oil-distribution wheel, and planetary reduction gear comprising such a wheel - Google Patents

Axially-partitioned oil-distribution wheel, and planetary reduction gear comprising such a wheel Download PDF

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Publication number
US10550723B2
US10550723B2 US16/073,197 US201716073197A US10550723B2 US 10550723 B2 US10550723 B2 US 10550723B2 US 201716073197 A US201716073197 A US 201716073197A US 10550723 B2 US10550723 B2 US 10550723B2
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oil
wheel
axis
cavity
sub
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US20190032514A1 (en
Inventor
Patrice Gedin
Pauline Marie Cecille AUTRAN
Cécile BRUOT
Guillaume Julien BECK
Alexis DOMBEK
Julie LEMOINE
Jordane Peltier
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Safran Transmission Systems SAS
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Safran Transmission Systems SAS
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Assigned to SAFRAN TRANSMISSION SYSTEMS reassignment SAFRAN TRANSMISSION SYSTEMS ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: AUTRAN, PAULINE MARIE CECILE, BECK, GUILLAUME JULIEN, BRUOT, CECILE, DOMBEK, Alexis, GEDIN, Patrice, LEMOINE, Julie, PELTIER, Jordane
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/18—Lubricating arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/04—Features relating to lubrication or cooling or heating
    • F16H57/042—Guidance of lubricant
    • F16H57/0427—Guidance of lubricant on rotary parts, e.g. using baffles for collecting lubricant by centrifugal force
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/04—Features relating to lubrication or cooling or heating
    • F16H57/0467—Elements of gearings to be lubricated, cooled or heated
    • F16H57/0479—Gears or bearings on planet carriers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/04—Features relating to lubrication or cooling or heating
    • F16H57/048—Type of gearings to be lubricated, cooled or heated
    • F16H57/0482—Gearings with gears having orbital motion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/40—Transmission of power
    • F05D2260/403—Transmission of power through the shape of the drive components
    • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
    • F05D2260/40311—Transmission of power through the shape of the drive components as in toothed gearing of the epicyclical, planetary or differential type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/98—Lubrication
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates in particular to a lubricant distribution wheel in a turbine engine and an epicyclic speed reduction gear, intended to equip in particular a turboprop engine or a turbojet engine of an aircraft.
  • a speed reduction gear typically consists of an inner planet gear (also called a sun gear) driven by an input shaft, for example a turbine shaft, an outer planet gear (also called a crown gear), coaxial with the inner planet gear, with planets meshing with both the inner and the outer planet gears, and a planet carrier whereon the planets are mounted to rotate.
  • an inner planet gear also called a sun gear
  • an outer planet gear also called a crown gear
  • the variation of the reduction ratio of such a speed reduction gear is obtained by changing the number of teeth of the sun gear, of the planets and the outer crown gear, and the by the architecture of the speed reduction gear.
  • lubricant wheels In turbine engines, lubricant wheels are known that have an axis around which an annular cavity extends:
  • said cavity is split into at least a first annular sub-cavity and a second annular sub-cavity, which:
  • a set of problems lies in supplying these members to be lubricated with pressure. This is particularly the case when said members are located within the rotating field (such as reduction gear bearings and teeth) and are supplied from a pump situated at a fixed reference point. Furthermore, the lubricant requirements are distributed differently depending on the operating phases of the reduction gear. Moreover, in order to limit losses, it is necessary to lubricate as close as possible to the needs of each of the members in question, which calls for adjustment of lubricant distribution.
  • the invention more particularly aims to provide a wheel solution that favours such adjustment, while allowing this supply of pressure to the members to be lubricated.
  • the aforementioned annular cavity has an overflow capacity at the location of said inner partition, so that an overflow of lubricant can take place, parallel to said axis, from the first sub-cavity into the second, and vice versa.
  • this wheel is designed to offer all or some of the following advantages:
  • this device intended for supplying oil to an assembly of pinions meshing on each other while rotating around a common axis of rotation (X), it is recommended that this device comprises:
  • the invention also relates to an epicyclic speed reduction gear as such, adapted to rotate around said common axis of rotation (X) and comprising:
  • the inner partition of the wheel in question is more distant from the axis of rotation (X) than the first and second lateral walls of this wheel are, so that an overflow of lubricant can take place, preferentially from one sub-cavity to another rather than outwards, parallel to said axis, from the first sub-cavity to the second sub-cavity and vice versa.
  • the invention also relates to a method of operation of the aforementioned oil supply device.
  • lubricant consumption is higher than at other times. Furthermore, it may be desirable to avoid splashing of the members lubricated by the wheel in question.
  • FIG. 1 shows a principle of a dual-flow turbojet
  • FIG. 2 shows a fan shaft epicyclic speed reduction gear, equipped with a lubrication system according to a possible embodiment, including details of supply of the lubricant to the reduction gear and within the latter, wherein the wheel is without the improvement according to the invention,
  • FIG. 3 is a cross-sectional perspective view of the above reduction gear, including the improvement according to the invention on the wheel,
  • FIG. 4 is a side view along the arrow IV and
  • FIGS. 5-7 show three states of filling of the above wheel.
  • a turbine engine 1 can be seen, such as a turbojet in this case, which conventionally comprises, globally and successively along the longitudinal X axis of the turbine engine, a fan S, a low-pressure compressor 1 a , a high-pressure compressor 1 b , a combustion chamber 1 c , a high-pressure turbine 1 d , a low-pressure turbine 1 e and an exhaust nozzle 1 h .
  • the high-pressure compressor 1 b and the high-pressure turbine 1 d are connected by a high-pressure shaft 2 and form with the later a high-pressure (HP) body.
  • the low-pressure compressor 1 a and the low-pressure turbine are connected by a low-pressure shaft 3 and form with the latter a low-pressure (LP) body.
  • LP low-pressure
  • the disc on which the blades of the fan S are mounted is driven by a fan shaft 4 , or LP trunnion, which is in turn directly driven by the LP shaft 3 , via an epicyclic reduction gear 10 .
  • the longitudinal X axis is the axis of rotation X of the turbine engine (around which the mobile blades of the fan S, of the compressors and of the turbines namely rotate). What is termed “radial” here is radial in relation to this X axis.
  • the blades of the fan S are borne by the fan shaft 4 , which is connected to the engine structure.
  • the downstream end of this fan shaft is fixed to the planet carrier 13 of the reduction gear 10 .
  • the LP shaft 3 is connected to the planet gear 11 of the reduction gear 10 by its ribs 7 .
  • FIG. 2 shows this and more generally, in a radial half cross-section, the upper part of the reduction gear 10 , with the lower part being located symmetrically in relation to the axis of rotation X.
  • the reduction gear 10 is fastened to one end of a support casing 22 by means of closure and support flanges 20 , which extend from the crown gear of the epicyclic reduction gear, thus securing the reduction gear to the fan shaft 2 and positioning it relative to the LP shaft 3 .
  • the enclosure of the reduction gear 10 is pressurised in a casing 24 .
  • the purpose of the pressurisation casing 24 is to create an enclosure around the reduction gear that is at a pressure higher than the surrounding pressure, which is placed under vacuum by a suction pump aspirating the oil in the reduction gear 10 .
  • the casing 24 surrounds the support casing 22 .
  • the reduction gear 10 is enclosed externally in its crown gear 14 , which is not movable in rotation and is fastened to the engine structure at the flanges 20 .
  • the reduction gear engages, on the one hand, on ribs 7 of the LP shaft 3 via the gear pinions of the planet gear 11 of the epicyclic reduction gear and on the other hand, on the fan shaft 4 , which is attached to the planet carrier 13 of this same epicyclic reduction gear.
  • the sun gear pinion 11 drives a series of planet pinions 12 , distributed regularly over the circumference of the reduction gear. These planets 12 also revolve around the X axis, rolling on the crown gear 14 , which is attached to the turbine engine structure by the support casing 22 .
  • a planet axis 16 linked to a planet carrier 13 , is positioned in the centre of each planet, with the planet rotating freely around this axis by means of a bearing, as illustrated. Rotation of the planets around their axis, owing to cooperation of their pinions with those of the crown gear 14 , results in rotation of the planet carrier 13 around the X axis and consequently around that of the fan shaft 4 connected to it.
  • the fan shaft 4 is driven by the planet carrier 13 by a series of centring fingers 17 , which extend axially from the downstream end of the fan shaft 4 .
  • the planet carrier 13 extends symmetrically on either side of the reduction gear, forming an enclosure in which a lubrication function can be implemented. Bushings 19 complete closing of this enclosure by blocking the latter at the planet axes 16 , on either side of the reduction gear.
  • the arrows in FIG. 2 show the path followed by the oil from a specific oil tank, known as the buffer tank 31 , to the pinions and bearings to be lubricated.
  • the buffer tank 31 is positioned next to the reduction gear, at the top so that the oil can flow by gravity towards the centre of the reduction gear.
  • This tank 31 is fed by a line 30 , originating from a main tank (not illustrated).
  • the oil flows into at least one injector 32 equipped with at least one jet 33 .
  • the oil emerges from the latter in the form of a jet 34 , which forms under the pressure produced jointly by the pressure of the feed pump and by the weight of the oil column located above the jet.
  • This jet 34 is oriented with a radial component directed towards the outside of the engine and ends in an oil distribution wheel 35 .
  • the wheel 35 forms a cavity for retaining the oil of the jet 34 .
  • This oil is driven in rotation by the wheel 35 , in the bottom of which it is pressurised under the action of centrifugal force.
  • Leading from the bottom of the wheel are respectively in 430 and 450 a series of lines for supplying oil to the various members to be lubricated. These lines, as illustrated based on FIG. 2 , comprise:
  • the oil that circulates in the first lines 43 penetrates into the internal cavity of each planet axis 16 .
  • the centrifugal force drives it into guide channels 44 crossing these axes radially.
  • These channels 44 emerge on the periphery of the planet axes 16 , at their bearings supporting the planets 12 , thereby lubricating these bearings.
  • the second lines 45 pass, from the bottom of the wheel 35 , between the planets 12 and branch into several channels 45 a , 45 b that convey the oil towards the gears formed on the one hand by the pinions of the planets 12 and those of the planet gear 11 and on the other hand by the pinions of the planets 12 and those of the crown gear 14 .
  • Each channel 45 a extends axially along the planet pinion, between the planet pinion 12 and the planet gear 11 .
  • the line 45 b which supplies the gear between the crown gear 11 and the planets 12 , projects its oil into the centre of the cylinder formed by each planet.
  • the oil will flow by gravity from the buffer tank 31 into the injector 32 . Under the pressure of the feed pump and the oil column located above the jet(s) 33 , the oil is ejected and recovered by the rotating wheel 35 into which it flows. It subsequently passes into the first and second lines 43 and 45 of each planet 12 .
  • the oil passing through the first line 43 enters the inner cavity of the corresponding planet pinion 12 and is subsequently simultaneously subjected to the previous centrifugal force field and the field due to the rotation of the planet pinion around its planet axis 16 . It crosses the thickness of the planet pinion 12 by means of the guide channels 44 and lubricates the bearing located between the planet 12 and its planet axis 16 .
  • the centrifugal acceleration field results in a pressure gradient along the pipe and ensures that this gradient results in a sufficiently high pressure (approximately 5 bars) at the bearing in order to be able to supply the latter.
  • the oil passing through the second line 45 branches between the second supply line 45 a of the planet gear and the second supply line 45 b of the planet-crown gear system.
  • the line 45 a ejects oil over the entire width of both pinions by means of its lubricating bar.
  • the line 45 b runs up the planet pinion to its gearing on the crown gear 14 and ends in a jet that lubricates this gearing.
  • the lubrication means will be capable of ensuring the supply of lubricant from a radially inner area of the wheel 35 to the corresponding teeth and bearings.
  • the wheel 35 in this case is a cylindrical cup with a U-shaped radial section, the opening of which faces the axis of rotation X. While the (each) injector 32 and its jet 33 are fixed, the wheel 35 is movable in rotation around the X axis. The opening of the U-shaped bottom of the wheel 35 is opposite the axis of rotation X and the jet, and the edges of the U are oriented towards this axis.
  • the axis of the wheel around which its inner annular cavity 37 extends is therefore the X axis. Furthermore, the cavity 37 is thus open radially towards the axis, X and bordered laterally by a first and a second wall 39 a , 39 b substantially radial to said axis, to receive the lubricant.
  • the first and second lines 43 , 45 for supplying lubricant to the bearings and teeth start from the cavity 37 , as illustrated.
  • the cavity 37 is split into annular sub-cavities 40 a , 40 b , two in number in this case.
  • These first and second sub-cavities are separated by an annular inner partition 38 substantially radial to the X axis and communicate with the first and second lines respectively.
  • the inner partition has, in relation to the respective bottoms 41 a , 41 b of the sub-cavities (these bottoms being laterally bordered by the first and second walls), a height h less than those (in this case identical, H) of the first and second walls 39 a , 39 b.
  • the radius R 1 along which the free end of each side wall 39 a or 39 b extends circumferentially is smaller than the radius R 2 along which the free end of the partition 38 extends circumferentially.
  • a module is defined as a subassembly of a turbine engine, the interfaces with the adjacent modules of which display geometric characteristics that are sufficiently precise to allow its separate delivery. Assembly of such modules makes it possible to build a complete engine, by reducing to a minimum the operations of balancing and pairing of the parts in interface.
  • module is achievable here, with its fan shaft 4 driven by a speed reduction gear of the type previously described.
  • the sub-cavities 40 a , 40 b of the wheel are supplied with oil via the means 33 so that an initial distribution of lubricating oil occurs in the cavity 37 via the partition 38 , with one (or a priori two) oil level(s) 47 a , 47 b being created accordingly in said sub-cavities (see FIG. 5 ).
  • one of these sub-cavities such as that marked 40 b in FIG. 6 , will even be oversupplied until the oil overflows into the adjacent sub-cavity, parallel to the X axis, over the partition 38 .
  • the pressure required to discharge the oil flow is in this case higher than the full wheel pressure (situation in FIG. 5 ).
  • the flow rate of the overflowing sub-cavity then no longer increases. However, the flow rate of the sub-cavity 40 a continues to increase. The distribution between the supply sections is therefore modified. If both sub-cavities are overflowing, the wheel overflows outwards ( FIG. 7 ).

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Details Of Gearings (AREA)
US16/073,197 2016-01-28 2017-01-27 Axially-partitioned oil-distribution wheel, and planetary reduction gear comprising such a wheel Active 2037-01-31 US10550723B2 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1650696 2016-01-28
FR1650696A FR3047279B1 (fr) 2016-01-28 2016-01-28 Rouet de distribution a repartition axiale et reducteur a train epicycloidal ainsi equipe
PCT/FR2017/050200 WO2017129926A1 (fr) 2016-01-28 2017-01-27 Rouet de distribution d'huile avec partitionnement axial et réducteur a train épicycloidal equipé d'un tel rouet

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US20190032514A1 US20190032514A1 (en) 2019-01-31
US10550723B2 true US10550723B2 (en) 2020-02-04

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US16/073,197 Active 2037-01-31 US10550723B2 (en) 2016-01-28 2017-01-27 Axially-partitioned oil-distribution wheel, and planetary reduction gear comprising such a wheel

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US (1) US10550723B2 (fr)
EP (1) EP3408504B1 (fr)
JP (1) JP7041064B2 (fr)
CN (1) CN108603414B (fr)
CA (1) CA3012406A1 (fr)
FR (1) FR3047279B1 (fr)
RU (1) RU2731149C2 (fr)
WO (1) WO2017129926A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11174756B2 (en) * 2018-03-20 2021-11-16 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine engine and method for introducing oil in a gearbox arrangement

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* Cited by examiner, † Cited by third party
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FR3066004B1 (fr) * 2017-05-04 2020-09-11 Safran Trans Systems Reducteur de vitesse debrayable
DE102017121739A1 (de) * 2017-09-19 2019-03-21 Rolls-Royce Deutschland Ltd & Co Kg Ölverteilungssystem mit wenigstens einem ersten drehbar ausgeführten Bereich und einem zweiten Bereich
FR3074552B1 (fr) 2017-12-06 2019-11-22 Safran Transmission Systems Couronne de reducteur de vitesse a train planetaire de turbomachine
FR3082266B1 (fr) * 2018-06-12 2020-06-19 Safran Aircraft Engines Dispositif de repartition d'huile pour un porte-satellites tournant d'un reducteur mecanique d'une turbomachine
FR3084429B1 (fr) * 2018-07-26 2020-11-13 Safran Trans Systems Dispositif du type reducteur ou differentiel pour une turbomachine d'aeronef
FR3087863B1 (fr) 2018-10-30 2020-12-11 Safran Trans Systems Roue dentee
FR3088977B1 (fr) 2018-11-23 2020-11-27 Safran Trans Systems Distributeur d’huile de lubrification pour un reducteur mecanique de turbomachine d’aeronef
FR3090786B1 (fr) * 2018-12-21 2020-12-04 Safran Trans Systems Distributeur d’huile de lubrification pour un reducteur mecanique de turbomachine d’aeronef
FR3092889B1 (fr) * 2019-02-14 2021-12-03 Safran Trans Systems Lubrification d’un porte-satellites pour un reducteur mecanique de turbomachine, en particulier d’aeronef
DE102019116974A1 (de) * 2019-06-24 2020-12-24 Rolls-Royce Deutschland Ltd & Co Kg Getriebe und Gasturbinentriebwerk
FR3103241B1 (fr) 2019-11-15 2021-12-17 Safran Trans Systems Rouet pour un porte-satellites de reducteur de vitesse a train epicycloïdal de turbomachine
FR3103240B1 (fr) 2019-11-15 2022-07-15 Safran Aircraft Engines Rouet pour un porte-satellites de reducteur de vitesse a train epicycloïdal de turbomachine
FR3103243B1 (fr) 2019-11-15 2022-07-15 Safran Trans Systems Rouet etage pour l’alimentation en huile d’un reducteur epicycloïdal ou planetaire.
US11203980B2 (en) 2020-01-17 2021-12-21 Unison Industries, Llc Air turbine starter with lubricated bearing assembly
FR3122715B1 (fr) 2021-05-06 2023-05-12 Safran Trans Systems Dispositif de lubrification amélioré pour réducteur de turbomachine.
FR3128753B1 (fr) 2021-11-03 2023-11-24 Safran Trans Systems Reducteur mecanique de vitesse pour une turbomachine d’aeronef

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3744246A (en) * 1972-03-02 1973-07-10 Du Pont Rotary closed rankine cycle engine with internal lubricating system
US6223616B1 (en) * 1999-12-22 2001-05-01 United Technologies Corporation Star gear system with lubrication circuit and lubrication method therefor
WO2010092263A1 (fr) 2009-02-16 2010-08-19 Snecma Lubrification et refroidissement d'un reducteur a train d'engrenages epicycloïdal
US20130225353A1 (en) 2012-02-23 2013-08-29 Snecma Device for lubricating an epicycloidal reduction gear
US8931285B2 (en) * 2010-10-12 2015-01-13 United Technologies Corporation Planetary gear system arrangement with auxiliary oil system

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2234035B (en) * 1989-07-21 1993-05-12 Rolls Royce Plc A reduction gear assembly and a gas turbine engine
DE4136040C1 (en) * 1991-11-01 1993-01-07 Mercedes-Benz Aktiengesellschaft, 7000 Stuttgart, De Epicyclic gear drive with disc clutch or brake - has oil guide flange between planetary gear front ends and drive path, dividing two annular chambers
FR2688574B1 (fr) * 1992-03-11 1994-05-06 Snecma Dispositif de filtration d'huile.
RU2347928C1 (ru) * 2007-06-04 2009-02-27 Открытое акционерное общество "Авиадвигатель" Редуктор привода однорядного вентилятора газотурбинного двигателя
WO2013124590A1 (fr) * 2012-02-23 2013-08-29 Snecma Dispositif de récupération de l'huile de lubrification d'un réducteur épicycloïdal

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3744246A (en) * 1972-03-02 1973-07-10 Du Pont Rotary closed rankine cycle engine with internal lubricating system
US6223616B1 (en) * 1999-12-22 2001-05-01 United Technologies Corporation Star gear system with lubrication circuit and lubrication method therefor
WO2010092263A1 (fr) 2009-02-16 2010-08-19 Snecma Lubrification et refroidissement d'un reducteur a train d'engrenages epicycloïdal
US8931285B2 (en) * 2010-10-12 2015-01-13 United Technologies Corporation Planetary gear system arrangement with auxiliary oil system
US20130225353A1 (en) 2012-02-23 2013-08-29 Snecma Device for lubricating an epicycloidal reduction gear

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11174756B2 (en) * 2018-03-20 2021-11-16 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine engine and method for introducing oil in a gearbox arrangement

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RU2731149C2 (ru) 2020-08-31
CA3012406A1 (fr) 2017-08-03
FR3047279B1 (fr) 2019-06-07
RU2018127196A3 (fr) 2020-03-12
JP2019508616A (ja) 2019-03-28
EP3408504B1 (fr) 2020-04-22
WO2017129926A1 (fr) 2017-08-03
US20190032514A1 (en) 2019-01-31
EP3408504A1 (fr) 2018-12-05
CN108603414B (zh) 2021-05-14
CN108603414A (zh) 2018-09-28
JP7041064B2 (ja) 2022-03-23
FR3047279A1 (fr) 2017-08-04
RU2018127196A (ru) 2020-03-02

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